CN113942641A - Elastic universal hinge - Google Patents
Elastic universal hinge Download PDFInfo
- Publication number
- CN113942641A CN113942641A CN202111176195.1A CN202111176195A CN113942641A CN 113942641 A CN113942641 A CN 113942641A CN 202111176195 A CN202111176195 A CN 202111176195A CN 113942641 A CN113942641 A CN 113942641A
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- Prior art keywords
- elastic
- star
- central
- elastic bearing
- universal hinge
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Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/32—Rotors
- B64C27/37—Rotors having articulated joints
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/32—Rotors
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/52—Tilting of rotor bodily relative to fuselage
Abstract
The application belongs to but not only is limited to helicopter rotor system design technical field, discloses an elasticity universal hinge, includes: the central part, the two centering elastic bearings, the star-shaped central elastic bearing and the mounting bolt; the central piece comprises a circular ring and three support arms which are integrally formed; the three support arms are arranged on the outer side of the circular ring at equal intervals; the star-shaped central elastic bearing is arranged in the central part circular ring and is not contacted with the side wall of the circular ring; the two centering elastic bearings are respectively fixed on the upper side and the lower side of the central part through bolts; the two centering elastic bearings are also connected with the star-shaped center elastic bearing through bolts; the middle part of the star-shaped central elastic bearing is provided with a first shaft hole; the middle parts of the two centering elastic bearings are also provided with second shaft holes; and a shaft connected with the universal hinge penetrates through the second shaft hole and the first shaft hole. The rotor motion requirements of the tilt rotor aircraft in three states of a helicopter mode, a fixed wing mode and a transition mode can be met, and static loads and dynamic loads of two flight states and a complex transition state can be transmitted and borne.
Description
Technical Field
The invention belongs to the technical field of helicopter rotor system design, and discloses an elastic universal hinge.
Background
With the development of helicopter technology, a high-speed rotorcraft capable of taking off and landing vertically becomes a hot spot of research. The tilt rotor aircraft combines the advantages of a helicopter and a fixed-wing aircraft, and is a dual-purpose high-technology product for military and civil use. The rotor of the tilt rotor aircraft is the main lifting surface and the control surface of the helicopter and is a key component of the tilt rotor aircraft. Research shows that only the universal hinge mechanism can meet the requirements of the functions and dynamics of the tilt rotor aircraft. At present, the existing universal hinge mechanisms include metal universal hinge mechanisms evolved from automobile cross universal hinge mechanisms, and also include complex elastic universal hinge mechanisms with V22 configuration of American military tilt rotorcraft and the like.
Disclosure of Invention
The elastic universal hinge is simple in structure, high in reliability and good in maintainability.
A resilient universal hinge, comprising: the central part, the two centering elastic bearings, the star-shaped central elastic bearing and the mounting bolt;
the central piece comprises a circular ring and three support arms which are integrally formed; the three support arms are arranged on the outer side of the circular ring at equal intervals;
the star-shaped central elastic bearing is arranged in the central part circular ring and is not contacted with the side wall of the circular ring;
the two centering elastic bearings are respectively fixed on the upper side and the lower side of the central part through bolts;
the two centering elastic bearings are also connected with the star-shaped center elastic bearing through bolts;
the middle part of the star-shaped central elastic bearing is provided with a first shaft hole;
a second shaft hole is also formed in the middle of each centering elastic bearing;
and a shaft connected with the universal hinge penetrates through the second shaft hole and the first shaft hole.
Furthermore, the star-shaped central elastic bearing is a triangular cylinder, and the middle part of the triangular cylinder is provided with a first shaft hole; three first through holes are formed in three vertexes of the triangular column; three hollow cylinders are respectively fixed in the three first through holes through elastic materials.
Furthermore, the root parts of the three support arms of the central part are provided with first bolt holes.
Further, the centering elastic bearing includes: the outer shell and the inner shell are connected through an elastic material;
a second shaft hole is formed in the inner shell;
a second bolt hole matched with the first bolt hole in position and size and a third bolt hole matched with the first through hole in position and size are formed in the shell;
the mounting bolt penetrates through the second bolt hole in the shell and the first bolt hole in the central piece to fix the shell and the central piece;
and the mounting bolt penetrates through the third bolt hole and the first through hole on the shell to connect the shell with the star-shaped central elastic bearing.
Further, the elastic material is formed by cross mixing of metal layers and rubber layer laminates.
Furthermore, the inner side wall of the central part circular ring is provided with three arc-shaped grooves at equal intervals, so that interference with the side wall of the first through hole at the vertex of the star-shaped central elastic bearing is avoided.
Furthermore, two centering elastic bearings of inner shell still are used for carrying out axial spacing to star type center elastic bearing for star type center elastic bearing is located the coplanar with the central component.
Furthermore, the outer side wall of the inner shell is a first spherical surface, and the inner side wall of the joint of the outer shell and the elastic material is a second spherical surface; the first spherical surface and the second spherical surface are concentric, and the sphere center is the middle point of the axis of the star-shaped central elastic bearing.
Has the advantages that:
the invention realizes complex rotor wing movement by designing a novel elastic universal hinge, can meet the rotor wing movement requirements of the tilt rotor wing aircraft in three states of a helicopter mode, a fixed wing mode and a transition mode, and can transmit and bear static loads and dynamic loads in two flight states and complex transition states.
Drawings
FIG. 1 is a component view of a resilient universal hinge;
FIG. 2 is a top view of a resilient gimbal hinge;
FIG. 3 is a top view of a resilient gimbal spider central resilient bearing;
FIG. 4 is a cross-sectional view of a resilient gimbaled central elastomeric bearing;
wherein, 1 central part, 2 centering elastic bearings, 3 star-shaped center elastic bearings, 4 rotor shafts and 5 mounting bolts.
Detailed Description
The invention is further illustrated by the following specific embodiments:
the invention relates to an elastic universal hinge which comprises a central part 1, a centering elastic bearing 2, a star-shaped center elastic bearing 3, a rotor shaft 4 and a mounting bolt 5.
Wherein, central authorities ' part 1 includes integrated into one piece's ring and equidistant three support arms that set up in the ring outside constitute, screw or paddle can be connected to three support arms, star type center elastic bearing 2 is installed in central authorities ' part 1 ring, 1 ring inside wall of central authorities ' part is equidistant to be equipped with three convex recess, avoid interfering and not contact with the ring lateral wall with 3 summit lateral walls of star type center elastic bearing, two centering elastic bearing 2 are fixed both sides about the central authorities ' part through construction bolt 5 respectively, two centering elastic bearing 2 still are connected with star type center elastic bearing 2 through the bolt.
The middle part of the star-shaped central elastic bearing 3 is provided with a first shaft hole, the middle parts of the two centering elastic bearings 2 are also provided with a second shaft hole, and the elastic universal hinge is connected with the rotor shaft 4 to penetrate through the second shaft hole and the first shaft hole.
The star-shaped central elastic bearing 3 is a triangular cylinder, three first through holes are formed in three vertexes of the triangular cylinder, a first spherical surface is arranged on the inner wall of each first through hole, three hollow cylinders are fixed in the three first through holes respectively through elastic materials, the outer side walls of the three hollow cylinders are second spherical surfaces, the elastic materials are elastic materials of metal and rubber laminated cross mixed structures and are connected, the first spherical surfaces and the second spherical surfaces share a common spherical center, and a plane formed by the three first spherical centers is a central plane of the star-shaped central elastic bearing 3.
The centering elastic bearing 2 comprises: outer shell, inner shell, just outer shell and inner shell pass through elastic material and connect, and wherein, elastic material is metal and the crossed mixed structure of rubber stromatolite, 2 inner shell lateral walls of centering elastic bearing are equipped with third sphere, outer shell and elastic material junction inside wall and are the fourth sphere, third sphere and fourth sphere are concentric, and the centre of sphere is the crossing point of star type central elastic bearing 3 planes and centering elastic bearing 2 axes. The shell of the centering elastic bearing 2 is provided with a second bolt hole matched with the position and the size of the first bolt hole and a third bolt hole matched with the position and the size of the first bolt hole, the mounting bolt penetrates through the second bolt hole in the shell and the first bolt hole in the central part to fix the shell and the first bolt hole arranged at the root part of the three support arms of the central part 1, and the mounting bolt penetrates through the third bolt hole in the shell and the first bolt hole to connect the shell and the star-shaped center elastic bearing 3.
When the rotor wing is in a working state, the two centering elastic bearings 2 are used as lift force transmission mechanisms and can limit the axial movement of elastic materials in the center 3 of the star-shaped center elastic bearing; when the propeller or the blade connected with the central piece 1 generates flapping motion, the plane where the central piece 1 is located generates inclination, and the motion is finally reflected by the deformation coordination of the elastic materials of the two centering elastic bearings 2 and the star-shaped central elastic bearing center 3; the power of the rotor torsional movement is transmitted from the rotor shaft 4 to the centering elastic bearing 2 through the star-shaped center elastic bearing 3, and the centering elastic bearing 2 is transmitted to the center piece 1.
The foregoing is merely a detailed description of the embodiments of the present invention, and some of the conventional techniques are not detailed. The scope of the present invention is not limited thereto, and any changes or substitutions that can be easily made by those skilled in the art within the technical scope of the present invention will be covered by the scope of the present invention. The protection scope of the present invention shall be subject to the protection scope of the claims.
Claims (8)
1. An elasticity universal hinge which characterized in that: the universal hinge includes: the central part, the two centering elastic bearings, the star-shaped central elastic bearing and the mounting bolt;
the central piece comprises a circular ring and three support arms which are integrally formed; the three support arms are arranged on the outer side of the circular ring at equal intervals;
the star-shaped central elastic bearing is arranged in the central part circular ring and is not contacted with the side wall of the circular ring;
the two centering elastic bearings are respectively fixed on the upper side and the lower side of the central part through bolts;
the two centering elastic bearings are also connected with the star-shaped center elastic bearing through bolts;
the middle part of the star-shaped central elastic bearing is provided with a first shaft hole;
a second shaft hole is also formed in the middle of each centering elastic bearing;
and a shaft connected with the universal hinge penetrates through the second shaft hole and the first shaft hole.
2. An elastic universal hinge according to claim 1, wherein: the star-shaped central elastic bearing is a triangular cylinder, and the middle part of the triangular cylinder is provided with a first shaft hole; three first through holes are formed in three vertexes of the triangular column; three hollow cylinders are respectively fixed in the three first through holes through elastic materials.
3. A resilient universal hinge according to claim 2, wherein: the root parts of the three support arms of the central part are provided with first bolt holes.
4. A resilient universal hinge according to claim 3, wherein: the centering elastic bearing includes: the outer shell and the inner shell are connected through an elastic material;
a second shaft hole is formed in the inner shell;
a second bolt hole matched with the first bolt hole in position and size and a third bolt hole matched with the first through hole in position and size are formed in the shell;
the mounting bolt penetrates through the second bolt hole in the shell and the first bolt hole in the central piece to fix the shell and the central piece;
and the mounting bolt penetrates through the third bolt hole and the first through hole on the shell to connect the shell with the star-shaped central elastic bearing.
5. An elastic universal hinge according to claim 4, wherein: the elastic material is formed by cross mixing of metal layers and rubber layer laminates.
6. An elastic universal hinge according to claim 5, wherein: the inner side wall of the central part circular ring is provided with three arc-shaped grooves at equal intervals, so that interference with the side wall of the first through hole at the vertex of the star-shaped central elastic bearing is avoided.
7. An elastic universal hinge according to claim 4, wherein: the two centering elastic bearings of the inner shell are also used for axially limiting the star-shaped central elastic bearing, so that the star-shaped central elastic bearing and the central part are positioned on the same plane.
8. An elastic universal hinge according to claim 7, wherein: the outer side wall of the inner shell is a first spherical surface, and the inner side wall of the joint of the outer shell and the elastic material is a second spherical surface; the first spherical surface and the second spherical surface are concentric, and the sphere center is the middle point of the axis of the star-shaped central elastic bearing.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111176195.1A CN113942641B (en) | 2021-10-09 | 2021-10-09 | Elastic universal hinge |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111176195.1A CN113942641B (en) | 2021-10-09 | 2021-10-09 | Elastic universal hinge |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN113942641A true CN113942641A (en) | 2022-01-18 |
| CN113942641B CN113942641B (en) | 2023-09-26 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202111176195.1A Active CN113942641B (en) | 2021-10-09 | 2021-10-09 | Elastic universal hinge |
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| CN (1) | CN113942641B (en) |
Citations (11)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN1214016A (en) * | 1996-03-18 | 1999-04-14 | 西科尔斯基飞机公司 | Axisymmetric elastomeric bearing assembly for helicopter rotors |
| CN106342057B (en) * | 2004-10-26 | 2007-06-20 | 南京航空航天大学 | A kind of depopulated helicopter |
| CN101936337A (en) * | 2010-09-10 | 2011-01-05 | 中国航空工业集团公司北京航空材料研究院 | Spherical elastic bearing for helicopter rotor wing and molding method thereof |
| CN101973399A (en) * | 2010-09-30 | 2011-02-16 | 南京航空航天大学 | Constant-speed universal hinged propeller hub for tilt-rotor aircraft |
| CN102458986A (en) * | 2009-05-06 | 2012-05-16 | K4A有限责任公司 | Constant velocity joint for helicopter rotors |
| CN106477040A (en) * | 2016-11-30 | 2017-03-08 | 中国直升机设计研究所 | Rotor driver is manipulated in a kind of axle |
| CN110683049A (en) * | 2019-09-16 | 2020-01-14 | 南京航空航天大学 | Hub device for small-sized tilt rotor aircraft |
| CN112046739A (en) * | 2020-08-06 | 2020-12-08 | 中国人民解放军总参谋部第六十研究所 | Rigid rotor hub of helicopter |
| CN112178052A (en) * | 2020-10-13 | 2021-01-05 | 株洲时代新材料科技股份有限公司 | Laminated rubber and metal elastic bearing |
| CN112268067A (en) * | 2020-10-16 | 2021-01-26 | 中国直升机设计研究所 | Elastic rod end bearing of helicopter rotor damper |
| CN112483539A (en) * | 2020-10-19 | 2021-03-12 | 南京航空航天大学 | Intelligent elastic bearing and control method |
Family Cites Families (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106342057C (en) * | 2004-10-26 | 2007-06-20 | 南京航空航天大学 | unmanned helicopter |
-
2021
- 2021-10-09 CN CN202111176195.1A patent/CN113942641B/en active Active
Patent Citations (11)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN1214016A (en) * | 1996-03-18 | 1999-04-14 | 西科尔斯基飞机公司 | Axisymmetric elastomeric bearing assembly for helicopter rotors |
| CN106342057B (en) * | 2004-10-26 | 2007-06-20 | 南京航空航天大学 | A kind of depopulated helicopter |
| CN102458986A (en) * | 2009-05-06 | 2012-05-16 | K4A有限责任公司 | Constant velocity joint for helicopter rotors |
| CN101936337A (en) * | 2010-09-10 | 2011-01-05 | 中国航空工业集团公司北京航空材料研究院 | Spherical elastic bearing for helicopter rotor wing and molding method thereof |
| CN101973399A (en) * | 2010-09-30 | 2011-02-16 | 南京航空航天大学 | Constant-speed universal hinged propeller hub for tilt-rotor aircraft |
| CN106477040A (en) * | 2016-11-30 | 2017-03-08 | 中国直升机设计研究所 | Rotor driver is manipulated in a kind of axle |
| CN110683049A (en) * | 2019-09-16 | 2020-01-14 | 南京航空航天大学 | Hub device for small-sized tilt rotor aircraft |
| CN112046739A (en) * | 2020-08-06 | 2020-12-08 | 中国人民解放军总参谋部第六十研究所 | Rigid rotor hub of helicopter |
| CN112178052A (en) * | 2020-10-13 | 2021-01-05 | 株洲时代新材料科技股份有限公司 | Laminated rubber and metal elastic bearing |
| CN112268067A (en) * | 2020-10-16 | 2021-01-26 | 中国直升机设计研究所 | Elastic rod end bearing of helicopter rotor damper |
| CN112483539A (en) * | 2020-10-19 | 2021-03-12 | 南京航空航天大学 | Intelligent elastic bearing and control method |
Also Published As
| Publication number | Publication date |
|---|---|
| CN113942641B (en) | 2023-09-26 |
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